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Grumman Mohawk

The Grumman OV-1 Mohawk is an armed military observation and attack aircraft that was designed for battlefield surveillance and light strike capabilities.

It has a twin turboprop configuration and carries two crew members in side-by-side seating.

The Mohawk was intended to operate from short, unimproved runways in support of United States Army forces.

The Mohawk began as a joint Army-Marine program through the then-Navy Bureau of Aeronautics (BuAer), for an observation/attack plane that would outperform the Cessna L-19 Bird Dog.

In June 1956, the Army issued Type Specification TS145, which called for the development and procurement of a two-seat, twin turboprop aircraft designed to operate from small, unimproved fields under all weather conditions.

It would be faster, with greater firepower, and heavier armour than the Bird Dog, which had proved vulnerable during the Korean War.

The Mohawk’s mission would include observation, artillery spotting, air control, emergency resupply, naval target spotting, liaison, and radiological monitoring.

The Navy specified that the aircraft must be capable of operating from small “jeep” escort class carriers (CVEs).

The DoD selected Grumman Aircraft Corporation’s G-134 design as the winner of the competition in 1957.

Marine requirements contributed an unusual feature to the design.

As originally proposed, the OF-1 could be fitted with water skis that would allow the aircraft to land at sea and taxi to island beaches at 20 knots (37 km/h).

Since the Marines were authorized to operate fixed-wing aircraft in the close air support (CAS) role, the mock-up also featured underwing pylons for rockets, bombs, and other stores.

The Air Force did not like the armament capability of the Mohawk and tried to get it removed, while the Marines did not want the Army’s sophisticated sensors.

However, the Navy then opted to spend the allocated budget on a fleet oil tanker instead, so the Marines had to drop out of the program in September 1957.

The Army continued with armed Mohawks and developed cargo pods that could be dropped from underwing hard points to resupply troops in emergencies.

The radar imaging capability of the Mohawk was to prove a significant advance in both peace and war.

The Side-Looking Airborne Radar (SLAR) could look through foliage and map terrain, presenting the observer with a film image of the earth below only minutes after the area was scanned.

In military operations, the image was split in two parts, one showing fixed terrain features, the other spotting moving targets.

The prototype (YAO-1AF) first flew on April 14, 1959.

The OV-1 entered production in October 1959.

In mid-1961, the first Mohawks to serve with U.S. forces overseas were delivered to the 7th Army at Sandhofen Airfield near Mannheim, Germany.

Before its formal acceptance, the camera-carrying AO-1AF was flown by Ralph Donnell on a tour of 29 European airfields to display it to the U.S. Army field commanders and potential European customers.

In addition to their Vietnam and European service, SLAR-equipped Mohawks began operational missions in 1963 patrolling the Korean Demilitarized Zone.

Germany and France showed early interest in the Mohawk, and Grumman actually signed a license production agreement with the French manufacturer Breguet Aviation in exchange for American rights to the Atlantic maritime patrol aircraft.

The very nature of the joint Army/Marine program had forced design compromises, such as ejection seats, that made the aircraft expensive and, sometimes, an openly resisted item in Army budgets.

Orders for the OV-1 stopped in Fiscal 1964, and the controversy in the Pentagon over the armed Mohawk peaked with a 1965 directive that prohibited the Army from operating armed fixed-wing aircraft.

Operational success in Vietnam led to additional Mohawk orders in 1966, and by 1968, five surveillance companies were operating in Southeast Asia.

The last of the Mohawk versions to enter production was the OV-1D with more powerful T53-701 engines, improved avionics, and interchangeable mission pallets that made it possible to switch the aircraft from infrared to SLAR configuration in about an hour.

The first four OV-1Ds were prototypes converted from earlier production airframes, and the first flew in 1969.

These were followed by 37 new-build aircraft, the last of which was delivered in December 1970.

Over the years, the mission and the aircraft underwent many changes and roughly 380 were built over all variants.

A four-engined Model 134E with tiltwings and tail ducted fan for control for VTOL was proposed to the Army but not built.

Model 134R was a tandem cockpit version offered to meet the Light Armed Reconnaissance Aircraft (LARA) requirement, but the NA300 was chosen instead becoming the OV-10.


YAO-1 (YOV-1A)

Initial prototypes.

OV-1A (AO-1AF)

Daylight observation variant.


Fitted with two additional Westinghouse J34 jet engines.

A non-flying, mixed-power, testbed, operated by the Pittsburgh Institute of Aeronautics.

OV-1B (AO-1BF)

SLAR variant.

OV-1C (AO-1CF)

IR reconnaissance variant.


Consolidated sensor variant.


OV-1As and OV-1Cs fitted with armament.


Quick Look ELINT machines.


Quick Look II ELINT machine.


Quick Look III ELINT machine.


Prototype for unproduced modernized variant.





41 ft 0 in (12.50 m)


48 ft 0 in (14.63 m)


12 ft 8 in (3.86 m)

Wing area

360 sq ft (33 m2)

Aspect ratio



NACA 2412

Empty weight

12,054 lb (5,468 kg)

Gross weight

15,544 lb (7,051 kg)

(Normal take-off weight, IR mission)

Max take-off weight

18,109 lb (8,214 kg) (SLAR mission)

Fuel capacity

276 US gal (230 imp gal; 1,040 L) internal fuel


2 × Lycoming T53-L-701 turboprops,

1,400 shp (1,000 kW) each


3-bladed Hamilton Standard Type 53C51-27 constant-speed propellers,

10 ft 0 in (3.05 m) diameter


Maximum speed

305 mph (491 km/h, 265 kn)

(IR mission)

Cruise speed

207 mph (333 km/h, 180 kn)

(Econ. cruise)

Stall speed

84 mph (135 km/h, 73 kn)

Never exceed speed

450 mph (720 km/h, 390 kn)


944 mi (1,519 km, 820 nmi) with external tanks

(SLAR mission)


4.35 hr

(SLAR mission)

Service ceiling

25,000 ft (7,600 m)

Rate of climb

3,466 ft/min (17.61 m/s)

(SLAR mission)

Take-off to 50 ft (15 m)

1,175 ft (358 m)

Landing run from 50 ft (15 m)

1,060 ft (320 m).





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